• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.527-528
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• 2012

DBD (Dielectric Barrier Discharge) plasma actuator was designed for aerodynamic drag reduction using plasma flow control, and the drag reduction was measured by wind-tunnel tests using 2D test model. At the zero wind velocity, the plasma flow control had no effect on the drag reduction because the flow separation and surface friction drag were not occurred. At the wind velocity of 2m/s, 9.7% of drag was reduced by the flow separation control. The drag reduction decreased as the wind velocity increased.

• Aerospace Engineering and Technology
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• v.12 no.2
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• pp.221-229
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• 2013

To achieve the best performance, the concept of drag reduced and power increased Human Power Aircraft(HPA) was presented by analyzing the HPAs in the world. To participate the '2012 HPA competition' in Korea, the streamlined fuselage and the simultaneous use of hands and feet were introduced. Furthermore the CFD analysis and power unit design were performed to verify the concept. In order to make the best use of streamlined fuselage effect, the fuselage shape design is important and to supply the hand power to the power unit, the control system design is important, also the test flight is required for validation.

• Journal of Advanced Marine Engineering and Technology
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• v.39 no.3
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• pp.243-247
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• 2015

The characteristics of the fluid force reduction of a square prism having a small triangular prism at the upstream side was investigated by measuring of lift and drag on the square prism The experimental parameters were the width ratios (H/B=0.2~0.6) of triangular prisms to the prism width and the gap ratios (G/B=0~3) between the square prism and the triangular prism. The drag reduction rate of the square prism was increased and then decreased with G/B in case of the same H/B, and was increased with H/B in case of the same G/B. The maximum drag reduction rate was represented by 78.5% at H/B=0.6 and G/B=1.5. The lift reduction rate of the square prism was hardly not affected by the width and gaps ratios, the average value was about 52.4%.

• Transactions of the Korean Society of Mechanical Engineers
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• v.17 no.5
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• pp.1262-1275
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• 1993

The drag reduction effect of a freely-rotatable splitter plate was experimentally investigated in the 2-D wake behind a circular cylinder. By arranging the splitter plate to be aparted with a certain gap from the cylinder, the splitter plate was able to be aligned itself automatically to the flow direction in the tested range of 6.2$\times$$10^3$$\times$$10^4$. As a result, it was proven that the self-adjustable splitter plate always reduced effectively the drag imposed on the body against any arbitrary flow directions. In a specific range of Reynolds numbers, the drag reduction effect was dependent not only on the length of the splitter plate but also on the gap distance between the plate and the trailing edge of the body. For a splitter plate with a specific length, there existed a unique optimum range of gap distance to obtain successfully the drag reduction effect, however, the optimum range of gap distance was dependent on Reynolds number.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.19 no.2
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• pp.71-76
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• 2018

Recently, various technologies have been developed for road facilities to reduce the load, some of which use technologies employing perforated plates for wind load reduction. Currently, there are no regulations concerning the drag coefficient of perforated plates for domestic road facilities. In the United States, the regulations regarding the drag coefficient of perforated plates in the 'Minimum design loads for buildings and other structures' were revised based on the studies of Letchford (2001) and Giannoulis (2012). In this study, a wind tunnel test was carried out to analyze the feasibility of applying regulations involving the perforated plates' drag coefficient. The results of the wind tunnel test and the drag coefficient used in the regulation were compared and analyzed. In addition, the reduction effect of the cross area of road signs calculated by applying the drag coefficient was analyzed. The results of the wind tunnel test and the value of the drag coefficient used in the regulation in the US were found to be very similar. Therefore, it was found that it is possible to apply the formula involving the drag coefficient of the perforated plate to the regulation and that the cross area of the perforated plate used for the post of the road sign is reduced by about 9.45% and that of the horizontal post by about 6.45%.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.26 no.9
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• pp.1302-1310
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• 2002

A direct numerical simulation in turbulent curved channel flow is performed. The drifting Taylor-Gortler vortices are identified by applying a conditional averaging. A new algorithm is proposed based on the wavelet transform of the wall information. A continuous wavelet transform with Marr wavelets is employed to decompose the flow signals at a chosen length scale. An active cancellation is applied to attenuate the Taylor-Gortler vortices and to reduce the wall skin friction.

• Journal of the Korean Society of Visualization
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• v.21 no.2
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• pp.8-13
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• 2023

The primary challenge in improving fuel efficiency and reducing air pollution for commercial vehicles is reducing their aerodynamic drag. Various flow control devices, such as cab-roof fairing, gap fairing, cab extender, and side skirt have been introduced to reduce drag, however, the drag reduction effect and applicability are different depending on each commercial vehicle model. To evaluate the fuel consumption of heavy vehicles, a comprehensive research approach, including drag force measurement, flow field analysis is required. This study investigated the effect of a cab extender, which installed rear region of cab, on a drag coefficient of commercial vehicle through wind tunnel experiments and CFD. The results showed that the cab extender significantly modified the flow structure around the vehicle, leading to 8.2% reduction in drag coefficient compared to the original vehicle model. These results would provide practical application for enhancing the aerodynamic performance and fuel efficiency of heavy vehicle.

• Journal of Advanced Marine Engineering and Technology
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• v.36 no.6
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• pp.808-813
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• 2012

The Characteristics of the drag reduction of a square prism having a detached splitter plate at the wake side were investigated by measuring of lift and drag on the square prism. The experimental parameters were the width ratios(H/B=0.5~1.5) of splitters to the prism width and the gap ratios (G/B=0~2) between the prism and the splitter plate. As the results the amplitude of the lift on the square prism having a detached splitter plate was remarkably decreased by comparison with the prototypical square prism. The drag reduction rate of the square prism was increased with H/B in case of the same G/B, and was increased and decreased with G/B in case of the same H/B. The maximum drag reduction rate was represented by 24.2% at H/B=1.5 and G/B=0.5.

• Proceedings of the Korea Water Resources Association Conference
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• 2010.05a
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• pp.1976-1981
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• 2010

하천사업이 자연친화적인 사업으로 변화하면서 친수성을 가진 다양한 형태들의 호안블록이 개발되고 있다. 호안블록의 다양성에 비해 유수에 대한 안정성을 검증할 수 있는 항력 양력계수, 상당조도 등의 수리특성인자에 대한 연구가 미진한 실정이다. 따라서 본 연구에서는 수리모형 실험을 통해 호안블록의 역학적인 특성을 분석하여 유수가 호안블록에 미치는 영향을 규명하였으며, 호안공법에 대한 수리모형 실험방법의 적용성을 모색하였다. 수리실험은 수로의 상류로부터 수류의 안정화가 이루어지는 9m 지점의 수로 바닥에 블록을 설치하였으며, 4분력계와 전자유속계를 이용하여 수리특성인자의 계측을 실시하였다. 단체실험은 형태가 다른 6개의 호안블록을 이용하여 실험을 실시하였으며, 단체실험결과에 의한 항력과 양력이 양호한 호안 4로 군체실험을 실시하였다. 군체 실험을 통해 상당조도가 0.163에서 0.165로 증가하는 것으로 확인되었으며, 상당조도의 증가에 따른 유속 저감 정도를 파악할 수 있었다.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.1
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• pp.25-32
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• 2015

Dielectric barrier discharge (DBD) plasma actuator was designed to reduce aerodynamic drag in a cylindrical model and wind tunnel test was performed at various wind velocities. In addition, computational fluid dynamics (CFD) analysis and flow visualization were used to investigate the effect of the plasma on the flow stream in the cylinderical model. At low wind velocity, the plasma actuator had no effects because flow separation did not appear. The aerodynamic drag was reduced by 14% at 14 m/s and by 27% at 17 m/s, respectively. It was confirmed by CFD analysis and flow visualization that the DBD plasma actuator decreased in pressure difference around the cylindrical model, thus decreasing the magnitude of wake vortex.